CN104416918A - Method for producing a reinforcement member of composite material - Google Patents
Method for producing a reinforcement member of composite material Download PDFInfo
- Publication number
- CN104416918A CN104416918A CN201410444598.3A CN201410444598A CN104416918A CN 104416918 A CN104416918 A CN 104416918A CN 201410444598 A CN201410444598 A CN 201410444598A CN 104416918 A CN104416918 A CN 104416918A
- Authority
- CN
- China
- Prior art keywords
- performing member
- coating
- bar
- mould
- alar part
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C37/00—Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
- B29C37/0067—Using separating agents during or after moulding; Applying separating agents on preforms or articles, e.g. to prevent sticking to each other
- B29C37/0075—Using separating agents during or after moulding; Applying separating agents on preforms or articles, e.g. to prevent sticking to each other using release sheets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/462—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/25—Solid
- B29K2105/253—Preform
- B29K2105/256—Sheets, plates, blanks or films
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
A method for producing a reinforcement member of composite material. The method includes producing a planar preform by stacking sheets of pre-impregnated fibers, heating the preform, and deforming the preform on a mold surmounted by an upper die whose shape confirms to a central portion of the reinforcement member to be obtained. The reinforcement member wings are in contact with the mold at two opposite lateral sides of the upper die after deformation. The deformed preform is also baked. Prior to deformation of the preform, a coating is applied promoting a sliding between the preform and the mold during the deformation. The coating comprises two tear-off strips superimposed on each other. A first tear-off strip is in the form of a pre-impregnated material in contact with the preform and a second tear-off strip is in the form of a dry material superimposed on the first tear-off strip.
Description
Technical field
The present invention relates to the method for composite material reinforced for the production of having Ω (omega) shape cross section.
Background technology
At aviation field, girth member is used to increase the mechanical performance of some element such as the panel such as forming fuselage.
In size and geometry, as shown in Figure 1A, the cross section of girth member 10 comprises the mid portion of U-shaped or V-arrangement on the one hand, comprise the alar part 16,16 ' forming abutment surface on the other hand in every side, mid portion has at least two inclined surfaces 12,12 ' connected by intermediate surface 14 alternatively.
By known methods, the girth member of composite comprises the fiber in embedded resin matrix.According to desirable feature, fiber must meet specific orientation.
According to known embodiment, the girth member of composite obtains by multi-disc or multilayer pre-impregnated fiber being covered on mould, and this mould comprises patrix, and the shape of patrix is suitable for the mid portion of girth member.
According to the first method of operating, manually blocks ofly the covering of flexible fiber sheet carries out, to guarantee the correct orientation of the fiber of different sheet, and be limited in the danger that bridge joint between fibre plate occurs in inclined surface 12, join domain between 12 ' and alar part 16,16 '.
Then, stacking fibre plate experience bake cycle.Even if this method of operating allows the inconsistent risk of restriction girth member, but tend to increase time and production cost due to manual override operation, institute can not be entirely satisfactory in this way.
At Covering domain, many tractor-drawn rakes allow automatically to cover, to reduce time and production cost.
But these machines are suitable for fibre plate to pile up in a flattened condition, and are not suitable for fibre plate to be stacked on patrix.
In the field producing composite material assembly, hot forming techniques is known, it comprises the smooth performing member using tractor-drawn rake producd fibers sheet, heat smooth performing member to the specified temp still allowing fibre plate to slide relative to each other lower than polymerization temperature, then performing member is made to be out of shape on mould, to obtain desirable form.
Due to this technological system cause the appearance of defect 18 (as shown in fig. 1b), particularly near inclined surface 12, join domain between 12 ' and alar part 16,16 ', so this technology is not suitable for production girth member.
Summary of the invention
Therefore, the object of the invention is the shortcoming overcoming prior art.For this reason, the present invention relates to a kind of method of producing composite material reinforced, wherein, the method comprises:
-produce smooth performing member by stacking pre-impregnated fiber sheet;
-heat described performing member;
-described performing member is out of shape on mould, described mould is covered by patrix, the shape of the shape of described patrix and the described mid portion of described girth member to be obtained adapts, and after distortion, the described alar part of described girth member contacts with described mould on every side of described patrix;
-make the performing member of distortion experience baking cycle;
-before described performing member distortion, applying coating, described coating promotes the slip between described performing member and described mould in described deformation process, described coating comprises two of mutually superposition and tears bar, and first of the pre impregnated material form contacted with described performing member is torn bar and is superimposed upon described first and tears second of dry substance form on bar and tear bar.
The program allows to obtain the girth member without any defect, adds the production cycle and reduces production cost.
Preferably, described coating cover each abutment surface at least partially and extend to the mid portion of smooth performing member respectively from transverse edge.Advantageously, described coating extends on the whole width of each alar part.According to an embodiment, described coating only extends on each alar part.
Accompanying drawing explanation
Other feature and advantage become obvious by by the description below of the present invention, and this description provides by means of only the mode of example by reference to the accompanying drawings, wherein:
Figure 1A shows the cross section of girth member;
Figure 1B shows the defective girth member of the tool sectional view under the microscope obtained according to the method for prior art;
Fig. 2 A shows and allows to obtain the smooth performing member representing girth member of the present invention;
Fig. 2 B shows the detail view of a part for the smooth performing member shown in Fig. 2 A;
Fig. 3, Fig. 4, Fig. 5, Fig. 6 are the sectional views of the different step illustrated schematically for the smooth performing member shown in Fig. 2 A that is shaped;
Fig. 7 is the sectional view of girth member in baking cycle obtained according to the present invention;
Fig. 8 is the microscope sectional view of the defective girth member of not tool according to the present invention's acquisition.
Detailed description of the invention
Fig. 7 shows girth member 20, and it comprises the mid portion of non-flat forms and the alar part 22,22 ' in every side, and alar part 22,22 ' can be pressed against by element to be reinforced, and mid portion and element separate to be reinforced are opened.
According to distortion, mid portion can have U-shaped or V-arrangement cross section.According to the embodiment shown in Fig. 7, mid portion comprises two inclined surfaces 24,24 ', and inclined surface 24,24 ' is connected by the surface 26 being basically parallel to alar part 22,22 ' alternatively.
The mid portion of girth member 20 comprises the lower surface 28 of convex and the upper surface 30 of spill, and lower surface 28 and upper surface 30 are opened by the separating distance of the thickness corresponding to girth member.
Each alar part 22,22 ' comprises abutment surface 32,32 ', and its lower surface 28 along mid portion extends continuously.The abutment surface 32,32 ' of girth member can be pressed against by parts to be reinforced.
In the following description, the full-size of girth member is longitudinally corresponded to.Lateral surfaces corresponds to the surface perpendicular to longitudinal direction, and it corresponds to the plane in the cross section in Fig. 2 A, 2B and Fig. 3 to Fig. 8.
The length of girth member corresponds to girth member size in the vertical.
Width corresponds to the size of girth member along a part for transverse plane.The spreading width of girth member corresponds to alar part 22,22 ' and form the summation of width on surface 24,24 ', 26 of mid portion of girth member.
As shown in Figure 2 A, the first step of the production method of girth member comprises the smooth performing member 34 making and have stacking pre-impregnated fiber sheet.
Smooth performing member 34 has the size substantially identical with the size of the girth member launched.In this way, smooth performing member 34 has the length substantially equal with the length of girth member, the width substantially equal with the spreading width of girth member and the thickness substantially equal with the thickness of untreated girth member (volume does not reduce).
Advantageously, smooth performing member 34 obtains by using automatic mulch-laying machine, to reduce time and production cost.
Fibre plate is stacked in girth member according to the desired orientation of fiber.
Tractor-drawn rake and accumulation technology are known to those skilled in the art, so no longer describe in further detail.
Smooth performing member 34 comprises two transverse edges 36,36 ' of the end corresponding to alar part 22,22 '.
Method for the production of girth member comprises the smooth performing member 34 of heating, and then make it be out of shape on mould 38, mould 38 comprises the flat surfaces covered by upper male mould 40, and the shape of upper male mould 40 corresponds to the lower surface 28 of the mid portion of girth member.After deformation, performing member 34 experiences baking cycle.This baking cycle can allow all or part of polymerization of girth member to be obtained.This knows for those skilled in the art, so be not described further.
According to feature of the present invention, the method is included in and goes up applying coating 42 at least partially at abutment surface 32,32 ' before smooth performing member 34 is out of shape, coating 42 can promote the slip between performing member 34 and mould 38 in deformation process, as shown in Figure 2A and 2B.
For each abutment surface, by coating being extended from transverse edge 36,36 ' to the mid portion of smooth performing member 34, coating 42 covers each abutment surface 32,32 ' at least partially.Advantageously, coating 42 extends on the whole surface of each abutment surface 32,32 ', or extends on the whole width of each alar part 22,22 '.
For each alar part 22,22 ', coating 42 comprises at least one and tears bar, and it is bonded to each abutment surface 32,32 '.
According to illustrated embodiment in more detail in Fig. 2 B, coating 42 comprises two of superposition and tears bar 44,44 ', and first of the pre impregnated material form contacted with smooth performing member 34 is torn bar 44 and is superimposed upon first and tears second of dry substance form on bar 44 and tear bar 44 '.
First tears bar 44 promotes coating 42 fixing to smooth performing member 34, second tears the slip that bar 44 ' promotes performing member 34 opposing mold 38 simultaneously.
The fiber tearing the material of bar 44 for pre-preg first must be compatible with the adhesive bonded on parts to be reinforced by abutment surface 32,32 '.According to embodiment, the first material tearing bar 44 is had epoxy resin by pre-preg.
Tear bar 44,44 ' peelable after baking.
Tear bar 44,44 ' manually to be placed.The heater blocks such as such as flatiron can be used to tear second bar 44 ' and are fixed to first and tear bar 44.
After performing member 34 is out of shape, coating 42 is removed.Preferably, coating 42 is removed after baking cycle.According to a method of operating, tear bar 44,44 ' and removed by stripping after baking cycle.
According to an embodiment, as shown in Figure 3, smooth performing member 34 is heated to the temperature of 80 DEG C by means of infra-red radiation by use lamp 46.
According to the embodiment shown in Fig. 3 to Fig. 6, in order to produce the distortion of performing member 34, need use instrument 48, instrument 48 comprises the mould 38, surrounding edge 50 and the framework 52 that are covered by upper male mould 40, and framework 52 coordinates with surrounding edge 50 and supports elastomeric bladder 54.
Instrument 48 is also included in the sealing device between surrounding edge 50 and framework 52, to obtain the sealed chamber 56 limited by mould 38, surrounding edge 50, framework 52 and capsule 54.
Instrument 48 also comprises the device for applying the pressure reduced in chamber 56.
Advantageously, upper male mould 40 is fixed removably and is attached to mould 38.In this way, after deformation, this assembly comprises the performing member of distortion, and upper male mould 40 can be disposed in pressure vessel to experience baking cycle.
No matter which kind of distortion, the device for the formation of smooth performing member 34 comprising device for heating performing member, having the upper male mould of the shape on the surface corresponding to girth member to be obtained, limiting the capsule of the chamber placing smooth performing member 34 and the device for applying the pressure reduced in the chamber together with mould.
The deformation stage composition graphs 3 to 6 of performing member 34 describes.
As shown in Figure 3, first smooth performing member 34 is heated.In this heating period, smooth performing member 34 can be placed on upper male mould 40.
When smooth performing member 34 is in 80 DEG C of temperature of needs, framework 52 is pressed against surrounding edge 50, to be enclosed in chamber 56 by smooth performing member 34.
Subsequently, as shwon in Figures 5 and 6, the pressure of reduction is applied in chamber 56, makes capsule 54 that performing member 34 is pressed against upper male mould 40 and mould 38.
In the stage of the pressure reduced, capsule 54 makes performing member 34 be out of shape, to be formed in two surfaces 58,58 ' with every side of the intermediate surface 26 of the tip contact of upper male mould 40.These two surfaces 58,58 ' little by little tunica 54 fold, until the end 36,36 ' of performing member 34 contacts mould 38, as shown in Figure 5.
Subsequently, inclined surface 24,24 ' and alar part 26,26 ' be little by little pressed against upper male mould 40 and mould 38 respectively, as shown in Figure 6.
Correspond to change from Fig. 5 to Fig. 6 inclined surface 24,24 ' and alar part 26,26 ' distortion stage in, end 36,36 ' so abutment surface 32,32 ' must slide on mould 38.
The coating 42 be coated in the region of abutment surface 32,32 ' promotes this slip, and prevents defect.In this way, as shown in Figure 8, fibre plate keeps being parallel to each other, particularly in the join domain of alar part and inclined surface.
When there is not coating 42, mould and have pre-impregnated fiber heating performing member between adhesive too many in the region of end 36,36 '.Like this, the translational motion of end 36,36 ' in distortion will produce skin resistance, and this is by the slip between blocking tab, and will cause the formation of defect 18, as shown in fig. 1b.
After deformation, the performing member be out of shape together with its coating 42 experiences baking cycle in the chamber reducing pressure on upper male mould 40, as shown in Figure 7, to obtain girth member 20.
After baking, coating 40 is removed by stripping.
Method permission of the present invention obtains the girth member without any defect by the smooth performing member using the automatic sheet mechanism of piling up to do.This technical scheme decreases time and production cost.
Claims (6)
1. the method for being produced composite material reinforced by stacking pre-impregnated fiber sheet, described girth member comprises mid portion and the alar part (22 in every side, 22 '), described alar part (22,22 ') there is abutment surface (32 respectively, 32 '), it is characterized in that, described method comprises:
-the smooth performing member (34) with transverse edge (36,36 ') is produced by stacking pre-impregnated fiber sheet;
-heat described performing member (34);
-make described performing member in the upper distortion of mould (38), described mould (38) is covered by patrix (40), the shape of the shape of described patrix (40) and the described mid portion of described girth member to be obtained adapts, after distortion, described alar part (22,22 ') contacts with described mould (38) in every side of described patrix (40);
-make the performing member of distortion experience baking cycle;
-before described performing member (34) distortion, applying coating (42), described coating (42) promotes the slip between described performing member (34) and described mould (38) in deformation process, described coating comprises two of mutually superposition and tears bar (44,44 '), tears bar (44) and tear second of dry substance form on bar (44) tear bar (44 ') to be superimposed upon described first with first of the pre impregnated material form contacted with described performing member (34).
2. method according to claim 1, it is characterized in that, for each abutment surface (32,32 '), by coating (42) being extended from described transverse edge (36,36 ') to the mid portion of smooth performing member (34), described coating (42) covers each abutment surface (32,32 ') at least partially.
3. method according to claim 2, is characterized in that, described coating (42) extends on the whole width of each alar part (22,22 ').
4. method according to claim 3, is characterized in that, described coating (42) is only in the upper extension of each alar part (22,22 ').
5. according to method in any one of the preceding claims wherein, it is characterized in that, the described first material tearing bar (44) is had epoxy resin by pre-preg.
6., according to method in any one of the preceding claims wherein, it is characterized in that, described in tear bar (44,44 ') and can peel off after baking.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1358419 | 2013-09-03 | ||
| FR1358419A FR3009997B1 (en) | 2013-09-03 | 2013-09-03 | METHOD FOR MANUFACTURING A STIFFENER IN COMPOSITE MATERIAL |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104416918A true CN104416918A (en) | 2015-03-18 |
| CN104416918B CN104416918B (en) | 2019-01-04 |
Family
ID=49510367
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410444598.3A Active CN104416918B (en) | 2013-09-03 | 2014-09-03 | Method for producing composite material reinforced part |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US9815226B2 (en) |
| CN (1) | CN104416918B (en) |
| FR (1) | FR3009997B1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108883586A (en) * | 2016-04-06 | 2018-11-23 | 罗尔斯·罗伊斯公司 | Method for manufacturing composite component |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101616634B1 (en) * | 2014-09-24 | 2016-04-29 | (주)엘지하우시스 | Seatback frame, method for producing the same and seatback for a vehicle |
| DE102015225467B4 (en) * | 2015-12-16 | 2019-12-19 | Airbus Defence and Space GmbH | Coated composite component and method for producing a coated composite component |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998038031A2 (en) * | 1997-02-27 | 1998-09-03 | Advanced Composites Group Ltd. | Improvements in or relating to moulding methods and moulded articles |
| US7032329B2 (en) * | 2004-01-07 | 2006-04-25 | Sakurai Sports Mfg. Co., Ltd. | Composite reinforced toecap and a method of making the same |
| CN101448626A (en) * | 2006-03-31 | 2009-06-03 | 空客西班牙公司 | A method for making a composite material structure by a retractable mould |
| WO2009118695A1 (en) * | 2008-03-27 | 2009-10-01 | Alenia Aeronautica S.P.A. | Method for manufacturing an elongated structural element made of composite material by means of forming and curing in an autoclave using a vacuum bag |
| US20130129957A1 (en) * | 2011-12-30 | 2013-05-23 | Cytec Technology Corp. | Peel Ply, Method of Surface Preparation and Bonding Composite Structures Using the Same |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6821368B2 (en) * | 2001-10-09 | 2004-11-23 | Lockheed Martin Corporation | Co-bonded joint with Z-pins |
| GB0719269D0 (en) | 2007-10-04 | 2007-11-14 | Airbus Uk Ltd | Method of moulding a charge |
| US8826957B2 (en) * | 2012-08-31 | 2014-09-09 | General Electric Company | Methods and systems for automated ply layup for composites |
-
2013
- 2013-09-03 FR FR1358419A patent/FR3009997B1/en active Active
-
2014
- 2014-08-27 US US14/469,999 patent/US9815226B2/en active Active
- 2014-09-03 CN CN201410444598.3A patent/CN104416918B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998038031A2 (en) * | 1997-02-27 | 1998-09-03 | Advanced Composites Group Ltd. | Improvements in or relating to moulding methods and moulded articles |
| US7032329B2 (en) * | 2004-01-07 | 2006-04-25 | Sakurai Sports Mfg. Co., Ltd. | Composite reinforced toecap and a method of making the same |
| CN101448626A (en) * | 2006-03-31 | 2009-06-03 | 空客西班牙公司 | A method for making a composite material structure by a retractable mould |
| WO2009118695A1 (en) * | 2008-03-27 | 2009-10-01 | Alenia Aeronautica S.P.A. | Method for manufacturing an elongated structural element made of composite material by means of forming and curing in an autoclave using a vacuum bag |
| US20130129957A1 (en) * | 2011-12-30 | 2013-05-23 | Cytec Technology Corp. | Peel Ply, Method of Surface Preparation and Bonding Composite Structures Using the Same |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108883586A (en) * | 2016-04-06 | 2018-11-23 | 罗尔斯·罗伊斯公司 | Method for manufacturing composite component |
| CN108883586B (en) * | 2016-04-06 | 2020-10-09 | 罗尔斯·罗伊斯公司 | Method for producing a composite component |
| CN112092415A (en) * | 2016-04-06 | 2020-12-18 | 罗尔斯·罗伊斯公司 | Method for producing a composite component |
| US11358307B2 (en) | 2016-04-06 | 2022-06-14 | Rolls-Royce Plc | Method for manufacturing a composite component |
| CN112092415B (en) * | 2016-04-06 | 2022-06-21 | 劳斯莱斯股份有限公司 | Method for producing a composite component |
| US11999079B2 (en) | 2016-04-06 | 2024-06-04 | Rolls-Royce Plc | Method for manufacturing a composite component |
Also Published As
| Publication number | Publication date |
|---|---|
| FR3009997B1 (en) | 2016-02-19 |
| CN104416918B (en) | 2019-01-04 |
| FR3009997A1 (en) | 2015-03-06 |
| US9815226B2 (en) | 2017-11-14 |
| US20150061187A1 (en) | 2015-03-05 |
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